Damping inlay for turbine blades

Patent metadata

Field	Value
Publication number	US-2016130953-A1
Application number	US-201514932313-A
Country	US
Kind code	A1
Filing date	Nov 4, 2015
Priority date	Nov 10, 2014
Publication date	May 12, 2016
Grant date	—

Abstract

The invention concerns a turbine blade comprising a surface, a recess within the surface, and a damping inlay within the recess. The damping inlay comprises a chamber with a damping material, for example particles. The damping inlay should substantially maintain the aerodynamic profile of the blade to enable normal operation. A further embodiment of the invention describes the method of manufacture of a turbine blade with a damping inlay. The method comprises the steps of manufacturing a turbine blade having a surface and a recess in the surface, and providing one or more damping inlays within the recess such that the damping inlay substantially maintains the aerodynamic profile of the blade, the damping inlay comprising a chamber and a damping material disposed within the chamber.

First claim

1 . A turbine blade comprising a surface, a recess within the surface, and a damping inlay within the recess, wherein the damping inlay comprises a chamber and a damping material disposed within the chamber, and the damping inlay substantially maintains the aerodynamic profile of the blade.

2 . A turbine blade according to claim 1 , wherein the turbine blade additionally comprises cooling means.

3 . A turbine blade according to claim 2 , wherein at least part of the cooling means is provided upstream of at least one damping inlay.

4 . A turbine blade according to claim 1 , wherein the damping material comprises one or more of a mass damper, a mass, a wire mesh, a powder, particles, or a liquid.

5 . A turbine blade according to claim 1 , wherein a plurality of damping inlays are provided for reduction of a plurality of damping modes.

6 . A damping inlay according to claim 1 , wherein the damping inlay additionally comprises a heat protective layer.

7 . A gas turbine comprising at least one turbine blade according to claim 1 .

8 . A method of making a turbine blade comprising the steps of
manufacturing a turbine blade, the turbine blade having a surface and a recess in the surface, and providing a damping inlay within the recess such that the damping inlay substantially maintains the aerodynamic profile of the blade, the damping inlay comprising a chamber and a damping material disposed within the chamber.

9 . The method of claim 8 , wherein the step of manufacturing a turbine blade comprises the steps of manufacturing a turbine blade and removing a portion of a surface of the turbine blade to create a recess in the surface.

10 . The method of claim 9 , wherein the portion of the surface of the turbine blade is removed using eroding, grinding or milling.

11 . The method of claim 8 , wherein providing the damping inlay comprises manufacturing a damping inlay and attaching the damping inlay within the recess.

12 . The method of claim 8 , wherein providing a damping inlay comprises at least partially filling the recess with a damping material and covering the recess to complete the damping inlay.

13 . The method of claim 8 , wherein the damping inlay is attached to the turbine blade using welding, brazing, soldering, an additive manufacturing method such as selective laser melting, glue or other adhesive means.

14 . The method of claim 8 , wherein the turbine blade is manufactured by casting, and the damping inlay is attached to the turbine blade during casting of the turbine blade.

15 . The method of claim 8 , wherein the damping inlay is manufactured, at least in part, by an additive manufacturing method such as selective laser melting, welding, forging or casting.

Assignees

• Alstom Technology Ltd

Inventors

• Brandl Herbert
• Beretta-Müller Arrigo

Classifications

• F05D2230/21

  by casting · CPC title

• F05D2230/25

  by forging · CPC title

• F05D2230/232

  by welding · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title